TCDS A53EU

Page 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 Rev. 37 30 6 29 27 29 27 12 35 27 33 21 32 37 38 37 36 Page 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 Rev. 22 27 29 26 27 27 35 30 30 33 24 32 28 38 37 31 36 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET No. A53EU This data sheet which is a part of Type Certificate No. A53EU prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder. ATR – GIE Avions de Transport Régional 1, Allée Pierre Nadot 31712 Blagnac Cedex France I. ATR42-200 (Transport Category Airplane) approved October 25, 1985. Engines. Two Pratt and Whitney Aircraft of Canada, Ltd., PW120 turboprops. Fuel. (a) The following fuels are eligible for engines MIL-T-5624 Grade JP5 AST-MD-1655 Grades JET A, JET A1 (PWC Service Bulletin No. 20 004 details approval conditions) (b) The following type of additives may be used in approved fuels: - oxidation inhibitors, - corrosion inhibitors, - thermal stability additives, - metal deactivators, - anti icing additives, - anti stating additives, - biocide additives. List of approved additives, approved concentrations and conditions of use are identified in PWC Service Bulletin no 20.004. A53EU Revision 38 ATR ATR42-200 ATR42-300 ATR42-320 ATR42-500 ATR72-101 ATR72-201 ATR72-102 ATR72-202 ATR72-211 ATR72-212 ATR72-212A August 27, 2026 A53EU, Rev 38 2 of 34 I. ATR42-200 (cont'd) Oil. The following oils are eligible for engines: - Synthetic type conforming to PWC specification PWA 521, Type II. PWC Service Bulletin 20 001 lists approved brand oils. Engine Limits. (PW-120) Operating limits with no unscheduled maintenance action required. Beyond these limits refer to maintenance manual. POWER SETTING TIME LIMIT TO ITT NH NP OIL PRESS OIL TEMP (%) (ºC) (%) (%) (PSI) (ºC) RESERVE TAKE OFF 5 minutes 105 816 100 101 55 to 65 0 to 125 (1) TAKE OFF 5 minutes 92 785 (4) 101 55 to 65 0 to 125 (1) MAXIMUM CONTINUOUS NONE 90 785 100 101 55 to 65 0 to 125 (1) GROUND IDLE 62 40 min -40 to 125 (1) min HOTEL MODE 785 40 min (2) 0 to 125 (1) STARTING 5 seconds 950 -40 min (3) TRANSIENT 10 mn 105 20 S 125 850 102 110 40 to 100 20 S 145.6 (5) 850 102 110 40 to 100 (1) Temperature up to 115ºC (120ºC in Hotel mode) is authorized without time limitation. 20 mn are authorized between 115ºC (120ºC in Hotel mode) and 125ºC. (2) For NH below 75%. NH above 75% requires 55 to 65 psi. (3) It may be assumed that before the first start of the day the oil temperature is the minimum temperature observed during the night. (4) Refer to AFM 2.04 p1A for NH limitation at take off. (5) If gearboxes incorporate SB 20316 or 20380. NOTE: Oil temperature must be maintained above 45ºC to ensure intake strut de-icing. Oil temperature must be maintained above 71ºC to ensure fuel anti-icing protection in absence of the low fuel temperature indication. Propellers. 2 Hamilton Sundstrand, four-bladed, 14 SF 5 (FAA TCDS P7NE). Blade: SFA 13( ) (see FAA TCDS P7NE) Propeller Limits. Diameter: 13 Ft. (+ 1/4 in., -3/16 in. manufacturing tolerance permissible) Pitch Setting at 42. in. of the axis: Feather: 86 degrees Flight Fine: 20 degrees Ground Fine: 7 degrees Full Reverse: -10 degrees Propeller (Np) – Take off 1200 R.P.M. Max. Continuous 1200 R.P.M. 3 of 34 A53EU, Rev 38 I. ATR42-200 (cont'd) Airspeed Limits (IAS). Maximum operating speed Vmo : 250 KIAS Maximum operating mach Mmo : 0.55 VA manoeuvering speed : 160 KIAS VFE Flaps 15o : 160 KIAS (170 KIAS with MOD. 1790) Flaps 30o : 145 KIAS (150 KIAS with MOD. 1790) Flaps 45o : 130 KIAS (Emergency only) VLO Gear extension : 160 KIAS Gear retraction : 160 KIAS VLE Landing gear extended : 160 KIAS (170 KIAS with MOD. 1790) VMC (Minimum control speed with the critical engine inoperative) - In flight - VMCA : 88.5 KIAS - Take Off - VMCG: 83 KIAS Tire speed limit (ground speed limit) 165 KIAS Center of Gravity (C.G.) Range. (Gear Extended) Forward Limit AFT Limit (% MAC) (% MAC) Take off and landing 15 36 Flight 12 38 Gear retraction has negligible effect on C.G. range. Maximum Weights. kg lb Taxi weight 15,770 34,770 Take Off weight 15,750 34,725 Landing weight 15,500 34,170 Zero Fuel weight 14,500 31,965 For aircraft incorporating ATR Modification 0863, weight limitations are modified as follows: kg lb Taxi weight 15,770 34,770 Take Off weight 15,750 34,725 Landing weight 15,500 34,170 Zero Fuel weight 15,200 33,510 Minimum Crew. 2 (pilot and co-pilot). Maximum Passengers. 46: 48 passenger capacity is approved with incorporation of modification 0481. 34: in COMBI configuration, with modification 0244 and with modification 0755 associated with the application of modifications 1073 and 1044. Maximum Baggage. Forward compartment - Maximum load 960 kg (2116 lb) 508 kg (1119 lb) with Mod 0481 Rear compartment - Maximum load 384 kg (846 lb) 768 kg (1693 lb) with Mod 0639 Fuel Capacity. Density 6,55 lb/US Gallon Usable Unusable lb US Gal 46.7 lb 2 x 4,960 2 x 757 A53EU, Rev 38 4 of 34 I. ATR42-200 (cont'd) Fuel Unbalance. Maximum fuel unbalance: 550 kg (1,212 lb) Oil Capacity. Engine oil capacity Usable 1,0 US Gallon/engine Total 4,7 US Gallon/engine Maximum Operating Altitude. 25,000 ft. II. ATR42-300 (Transport Category Airplane) approved October 25, 1985. Engines. Two Pratt and Whitney Aircraft of Canada, Ltd, PW120 turboprops. Fuel. (a) The following fuels are eligible for engines MIL-T-5624 Grade JP5 AST-MD-1655 Grades JET A, JET A1 (PWC Service Bulletin no 20 004 details approval conditions) (b) The following types of additives may be used in approved fuels: - oxidation inhibitors, - corrosion inhibitors, - thermal stability additives, - metal deactivators, - anti icing additives, - anti stating additives, - biocide additives. List of approved additives, approved concentrations and conditions of use are identified in PWC Service Bulletin no 20.004. Oil. The following oils are eligible for engines: - Synthetic type conforming to PWC specification PWA 521, Type II. PWC Service Bulletin 20 001 lists approved brand oils. Engine Limits. (PW-120) Operating limits with no unscheduled maintenance action required. Beyond these limits refer to maintenance manual. POWER SETTING TIME LIMIT TO ITT NH NP OIL PRESS OIL TEMP (%) (ºC) (%) (%) (PSI) (ºC) RESERVE TAKE OFF 5 minutes 105 816 100 101 55 to 65 0 to 125 (1) TAKE OFF 5 minutes 92 785 (4) 101 55 to 65 0 to 125 (1) MAXIMUM CONTINUOUS NONE 90 785 100 101 55 to 65 0 to 125 (1) GROUND IDLE 62 40 min -40 to 125 (1) min HOTEL MODE 785 40 min (2) 0 to 125 (1) STARTING 5 seconds 950 -40 min (3) TRANSIENT 10 mn 105 20 S 125 850 102 110 40 to 100 20 S 145.6 (5) 850 102 110 40 to 100 5 of 34 A53EU, Rev 38 II. ATR42-300 (cont'd) (1) Temperature up to 115ºC (120ºC in Hotel mode) is authorized without time limitation. 20 mn are authorized between 115ºC (120ºC in Hotel mode) and 125ºC. (2) For NH below 75%. NH above 75% requires 55 to 65 psi. (3) It may be assumed that before the first start of the day the oil temperature is the minimum temperature observed during the night. (4) Refer to AFM 2.04 p1A for NH limitation at take off. (5) If gearboxes incorporate SB 20316 or 20380. NOTE: Oil temperature must be maintained above 45ºC to ensure intake strut de-icing. Oil temperature must be maintained above 71ºC to ensure fuel anti-icing protection in absence of the low fuel temperature indication. Propellers. 2 Hamilton Sundstrand, four-bladed, 14 SF 5 (FAA TCDS P7NE). Blade: SFA 13( ) (see FAA TCDS P7NE) Propeller Limits. Diameter: 13 FT. (+ 1/4 in., -3/16 in. manufacturing tolerance permissible.) Pitch Setting at 42 in. of the axis: Feather : 86 degrees Flight Fine: 20 degrees Ground Fine: 7 degrees Full Reverse: -10 degrees Propeller (Np) – Take off 1200 R.P.M. Max. Continuous 1200 R.P.M. Airspeed Limits (IAS). Maximum operating speed VMO : 250 KIAS Maximum operating mach VMO : 0.55 VA manoeuvering speed : 160 KIAS VFE Flaps 15o : 160 KIAS (170 KIAS with MOD.1790) Flaps 30o : 145 KIAS (150 KIAS with MOD.1790) Flaps 45o : 130 KIAS (Emergency only) VLO Gear extension : 160 KIAS Gear retraction : 160 KIAS VLE Landing gear extended : 160 KIAS (170 KIAS with MOD.1790) VMC (Minimum control speed with the critical engine inoperative) - In flight - VMCA : 88.5 KIAS - Take off - VMCG : 83 KIAS Tire speed limit (ground speed limit) : 165 KIAS Center of Gravity (C.G.) Range. (Gear Extended) Forward Limit AFT Limit (% MAC) (% MAC) Take off and landing 15 36 Flight 12 38 For aircraft incorporating ATR Modification 0951 (Service Bulletin No. ATR42-08-0001), C.G. range is modified as follows: Forward Limit AFT Limit (% MAC) (% MAC) Take off: 16,150 kg. G.W. 15 36 16,700 kg. G.W 17 32 Landing: 16,000 kg. G.W. 15 36 16,400 kg. G.W. 17 32 Flight: 12 38 (Straight line variation between points). Gear retraction has negligible effect on C.G. range. A53EU, Rev 38 6 of 34 II. ATR42-300 (cont'd) Maximum Weights. kg lb Taxi weight 16,170 35,645 Take Off weight 16,150 35,605 Landing weight 16,000 35,270 Zero Fuel weight 14,800 32,625 For aircraft incorporating ATR Modification 0863, weight limitations are modified as follows: Taxi weight 16,170 35,645 Take Off weight 16,150 35,605 Landing weight 16,000 35,270 Zero Fuel weight 15,200 33,510 For aircraft incorporating ATR Modification 0951 (ATR Service Bulletin No. ATR42-08-0001), weight limitations are modified as follows: Taxi weight 16,720 36,870 Take Off weight 16,700 36,825 Landing weight 16,400 36,160 Zero Fuel weight 15,200 33,510 Minimum Crew. 2 (pilot and co-pilot). Maximum Passengers. 46: 48 passenger capacity is approved with incorporation of modification 0481. 34: in COMBI configuration, with modification 0244 and with modification 0755 associated with the application of modifications 1073 and 1044. Maximum Baggage. Forward compartment - Maximum load 2,045 lb Rear compartment - Maximum load 952 lb. Fuel Capacity. Density 6.55 lb/US Gallon Usable Unusable lb US Gal 46.7 lb 2 x 4,960 2 x 757 Fuel Unbalance. Maximum fuel unbalance: 550 kg (1,212 lb) Oil Capacity. Engine oil capacity Usable 1.0 US Gallon/engine Total 4.7 US Gallon/engine Maximum Operating Altitude. 25,000 ft. III. ATR42-320 (Transport Category Airplane) approved August 25, 1988. Engines. Two Pratt and Whitney Aircraft of Canada, Ltd, PW121 turboprops. Fuel. (a) The following fuels are eligible for engines MIL-T-5624 Grade JP5 AST-MD-1655 Grades JET A, JET A1 (PWC Service Bulletin no 20 004 details approved conditions). 7 of 34 A53EU, Rev 38 III. ATR42-320 (cont'd) Fuel. (cont'd) (b) The following types of additives may be used in approved fuels: - oxidation inhibitors, - corrosion inhibitors, - thermal stability additives, - metal deactivators, - anti icing additives, - anti stating additives, - biocide additives. List of approved additives, approved concentrations and conditions of use are identified in PWC Service Bulletin no 20.004. Oil. The following oils are eligible for engines: - Synthetic type conforming to PWC specification PWA 521, Type II. PWC Service Bulletin 20 001 lists approved brand oils. Engine Limits. (PW-121) Operating limits with no unscheduled maintenance action required. Beyond these limits refer to maintenance manual. POWER SETTING TIME LIMIT TO ITT NH NP OIL PRESS OIL TEMP (%) (ºC) (%) (%) (PSI) (ºC) RESERVE TAKE OFF 5 minutes 107,2 816 100 101 55 to 65 0 to 125 (1) TAKE OFF 5 minutes 92,9 (5) (4) 101 55 to 65 0 to 125 (1) MAXIMUM CONTINUOUS NONE 92,9 800 100 101 55 to 65 0 to 125 (1) GROUND IDLE 62 40 min -40 to 125 (1) min HOTEL MODE 785 40 min (2) -40 to 125 (1) STARTING 5 seconds 950 -40 min (3) TRANSIENT 10 mn 107,2 20 S 119.7 850 102 110 40 to 100 20 S 138,7 (6) 850 102 110 40 to 100 (1) Temperature up to 115ºC (120ºC in Hotel mode) is authorized without time limitation. 20 mn are authorized between 115ºC (120ºC in Hotel mode) and 125ºC. (2) For NH below 75%. NH above 75% requires 55 to 65 psi. (3) It may be assumed that before the first start of the day the oil temperature is the minimum temperature observed during the night. (4) Refer to AFM 2.04 p1A for NH limitation at take off. (5) If gearboxes incorporate SB 20316 or 20380. NOTE: Oil temperature must be maintained above 45ºC to ensure intake strut de-icing. Oil temperature must be maintained above 71ºC to ensure fuel anti-icing protection in absence of the low fuel temperature indication. Propellers. 2 Hamilton Sundstrand, four-bladed, 14 SF 5 (FAA TCDS P7NE). Blade: SFA 13( ) (see FAA TCDS P7NE) Propeller Limits. Diameter: 13 FT. (+ 1/4 in., -3/16 in. manufacturing tolerance permissible) Pitch Setting at 42. in. of the axis: Feather: 86 degrees Flight Fine: 20 degrees Ground Fine: 7 degrees Full Reverse: -10 degrees Propeller (Np) – Take off 1200 R.P.M. Max Continuous 1200 R.P.M. A53EU, Rev 38 8 of 34 III. ATR42-320 (cont'd) Airspeed Limits (IAS). Maximum operating speed VMO : 250 KIAS Maximum operating mach VMO : 0.55 VA manoeuvering speed : 160 KIAS VFE Flaps 15o : 160 KIAS (170 KIAS with MOD.1790) Flaps 30o : 145 KIAS (150 KIAS with MOD.1790) Flaps 45o : 130 KIAS (Emergency only) VLO Gear extension : 160 KIAS Gear retraction : 160 KIAS VLE Landing gear extended : 160 KIAS (170 KIAS with MOD.1790) VMC (Minimum control speed with the critical engine inoperative) - In flight - VMCA : 90.5 KIAS - Take off - VMCG: 84.5 KIAS Tire speed limit (ground speed limit): 165 KIAS Center of Gravity (C.G.) Range. (Gear Extended) Forward Limit AFT Limit (% MAC) (% MAC) Take off and landing 15 36 Flight 12 38 For aircraft incorporating ATR Modification 0951 (Service Bulletin No. ATR42-08-0001), C.G. range is modified as follows: Forward Limit AFT Limit (% MAC) (% MAC) Take off: 16,150 kg. G.W. 15 36 16,700 kg. G.W 17 32 Landing: 16,000 kg. G.W. 15 36 16,400 kg. G.W. 17 32 Flight: 12 38 (Straight line variation between points). Gear retraction has negligible effect on C.G. range. Maximum Weights. kg lb Taxi weight 16,170 35,645 Take Off weight 16,150 35,605 Landing weight 16,000 35,270 Zero Fuel weight 14,800 32,625 For aircraft incorporating ATR Modification 0863, weight limitations are modified as follows: kg lb Taxi weight 16,170 35,645 Take Off weight 16,150 35,605 Landing weight 16,000 35,270 Zero Fuel weight 15,200 33,510 For aircraft incorporating ATR Modification 0951 (ATR Service Bulletin No. ATR42-08-0001), weight limitations are modified as follows: kg lb Taxi weight 16,720 36,870 Take Off weight 16,700 36,825 Landing weight 16,400 36,160 Zero Fuel weight 15,200 33,510 9 of 34 A53EU, Rev 38 III. ATR42-320 (cont'd) Minimum Crew. 2 (pilot and co-pilot). Maximum Passengers. 46: 48 passenger capacity is approved with incorporation of modification 0481. 34: in COMBI configuration, with modification 0244 and with modification 0755 associated with the application of modifications 1073 and 1044. Maximum Baggage. Forward compartment - Maximum load 2,045 lb. Rear compartment - Maximum load 952 lb. Fuel Capacity. Density 6.55 lb/US Gallon Usable Unusable lb US Gal 46.7 lb 2 x 4,960 2 x 757 Fuel Unbalance. Maximum fuel unbalance: 550 kg (1,212 lb) Oil Capacity. Engine oil capacity Usable 1.0 US Gallon/engine Total 4.7 US Gallon/engine Maximum operating altitude. 25,000 ft. IV. ATR42-500 (Transport Category Airplane) approved May 13, 1996. Engines. Two Pratt and Whitney Aircraft of Canada, Ltd, PW127E turboprops or PW127F by SB ATR42-72-0008 or PW127M by SB ATR42-72-0010 or in production line from aircraft serial number 675 (inclusive) or PW127XT-M with MOD 10016. Engine models PW127M and PW127XT-M are interchangeable and mixable with MOD 10302, with conditions (refer to relevant approved Airplane Flight Manual). Fuel. (a) The following fuels are eligible for engines MIL-T-5624 Grade JP5 AST-MD-1655 Grades JET A, JET A1 (PWC Service Bulletin No. 20 004 details approved conditions). (b) The following types of additives may be used in approved fuels: - oxidation inhibitors, - corrosion inhibitors, - thermal stability additives, - metal deactivators, - anti icing additives, - anti stating additives, - biocide additives. List of approved additives, approved concentrations and conditions of use are identified in PWC Service Bulletin No. 20.004. Oil. The following oils are eligible for engines: - Synthetic type conforming to PWC specification PWA 521, Type II. PWC Service Bulletin 20 001 lists approved brand oils. A53EU, Rev 38 10 of 34 IV. ATR42-500 (cont'd) Engine Limits. (PW-127E) Operating limits with no unscheduled maintenance action required. Beyond these limits refer to maintenance manual. Engine rating Time limit Torque % ITT (C) NH % NL % NP % Oil Pressure (Psi) Oil temperature (1) (C) Reserve Take off 10 mn* 100** 800 103.2 104.2 101 55 to 65 0 to 125 Take off 5 mn 90** 740 to 765 101.9 101.4 101 55 to 65 0 to 125 Maximum Continuous - 100** 800 103.2 104.2 101 55 to 65 0 to 125 Ground idle 66 mini 40 mini *** -40 to 125 Hotel mode 715 55 to 65 0 to 125 Starting 5 sec. 950 -54 mini Transient 20 sec. 5 sec. 20 mn 137.5 840 104.3 106.5 106 **** 120 40 to 100 140 * Time beyond 5 mn is linked to actual single engine operations only. ** Value linked 100% NP. *** Associated with NH ratings lower than 75 %. **** Permissible for completion of flight provided torque does not exceed 85% during climb and 84 % during cruise (1) Oil temperature must be maintained above 45C to ensure protection for the engine air inlet against ice accumulation. Propellers. 2 Hamilton Sundstrand, six-bladed, 568 F -1 (FAA TCDS P8BO). Blade: R 815 505( ) (see FAA TCDS P8BO) Propeller Limits. Diameter: 13 FT. (+ 1/4 in., -3/16 in. manufacturing tolerance permissible) Pitch Setting at 58 in. of the axis: Feather : 78.5 degrees Flight Fine: 14 degrees Ground Fine: 0 degrees Full Reverse: -14 degrees Propeller (Np) - Take off 1200 R.P.M. Max Continuous 1200 R.P.M. Airspeed Limits (IAS). Maximum operating speed VMO : 250 KIAS Maximum operating mach VMO : 0.55 VA manoeuvering speed : 160 KIAS VFE Flaps 15 : 170 KIAS/180 KIAS (*) Flaps 25 : 160 KIAS Flaps 35 : 150 KIAS VLO Gear extension : 170 KIAS Gear retraction : 160 KIAS VLE Landing gear extended : 180 KIAS VMC (Minimum control speed with the critical engine inoperative) - In flight - VMCA : 98.5 KIAS (SL, ISA) - Take off - VMCG : 95 KIAS (SL, ISA) Tire speed limit (ground speed limit) : 165 KIAS (*) with embodiment of modification 4462 11 of 34 A53EU, Rev 38 IV. ATR42-500 (cont'd) Center of Gravity (C.G.) Range. (Gear Extended) Forward Limit (% MAC) AFT Limit (% MAC) Take off 16,150 kg. G.W. 18,600 kg. G.W. 15 21 34 34 Landing: 16,150 kg. G.W. 18,300 kg. G.W. 15 20.3 34 34 Flight: 16,150 kg. G.W. 18,600 Kg. G.W. 12 18 36 36 (Straight line variation between points). Gear retraction has negligible effect on C.G. range. Maximum Weights. kg lb Taxi weight 18,770 41,380 Take Off weight 18,600 41,005 Landing weight 18,300 40,344 Zero Fuel weight 16,700 36,817 Minimum Crew. 2 (pilot and co-pilot). Maximum Passengers. 60 as limited by emergency exits configuration. Maximum Baggage. Forward compartment - Maximum load 928 kg (2,046 lb) Rear compartment - Maximum load 768 kg (1,693 lb) Fuel Capacity. Density 6.55 lb/US Gallon Usable Unusable lb US Gal 46.7 lb 2 x 4,960 2 x 757 Fuel Unbalance. Maximum fuel unbalance: 550 kg (1,212 lb) Oil Capacity. Engine oil capacity Usable 1.0 US Gallon/engine Total 4.7 US Gallon/engine Maximum Operating Altitude. 25,000 ft. (a) ATR42-500 Model “600 version” Definition (Approved April 4, 2013) The ATR42-500 “600 version” designation does not correspond to a model designation. This is only a commercial designation for an ATR42-500 on which Major modifications 5948, 6521, 6230, and 6233 have been embodied during production. Modification 5948 design change consist of the installation of a New Avionics Suite (NAS) and contains the following modifications: • Integrated Avionics Display – 5 IADs including FMS and RMS functions • Core Avionics Cabinet – CAC (including AFCS, DCA, FWS & CMA functions) (x2) • AFCS servo motors + Power Trim Box • AHRS (x2) • ADC (x2) • GPS (x1), a 2nd GPS is optional • Radio Altimeter (x1) • T²CAS (ACAS + TAWS) (x1) • Transponders (x2) • Control panels • MCDU (x2) A53EU, Rev 38 12 of 34 • Integrated Electronic Stand-by Instrument (x1) • Radio Com (VHF, HF wiring provision) (x2) • Radio Nav (VOR, ILS, MKR, ADF, DME) (x2) (2nd ADF and 2nd DME are optional) • Clocks (x2) • Ambient Pressure Sensor (x1) Modification 6521 adds NAS software version L2B2 Modification 6230 adapts the NAS on the ATR42-500 Modification 6233 installs a new fuel gauging system in kilograms DATA PERTINENT TO ATR42-200, -300, -320, -500 MODELS Datum. Station 0 (93 inches forward of fuselage nose). MAC. 90 inches (leading edge of MAC: STA 450) Leveling Means. Inclinometer on the cabin seat track rails. Maximum Control Surface Deflections. ATR 42-200/-300/-320 ATR 42-500 UP DOWN UP DOWN Aileron 14  0.5 14  0.5 14  0.5 14° ± 0.25° *** 14  0.5 14° ± 0.25° *** Aileron trim 13.75  0.7 10.15  0.5 4.5  0.4 6.7° ± 0.4° *** 4.5  0.4 6.7° ± 0.4° *** Elevator + 1 25 + 0 + 1 15 - 0.6 + 1 23 + 0 + 1 13 - 0.6 Elevator trim 5.2  0.3 8.4  0.4 4  0.3 9  0.4 Rudder : + 1.5 structural stops (damper removed)  31.5 - 0 stop included in damper  30  1